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  • AERODYNAMICS  (958)
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  • 1980-1984  (485)
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  • 1
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Subjects on planetary flight missions, supporting technology, microbial release probabilities, heat sterilization cycles
    Schlagwort(e): BIOSCIENCES
    Materialart: NNING, EVALUATION, AND ANAL. STUDIES IN PLANETARY QUARANTINE AND SPACECRAFT STERILIZATION 15 JUN. 1970 (SEE N70-35042 19-04) 19-04/
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  • 2
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Conflicting sensory data relating to spatial orientation from visual, vestibular, and somatosensory systems inducing motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 45-52
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  • 3
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Mathematical model for short-term adaptation to vestibular stimuli in relation to angular velocity of nystagmus and angular velocity of head rotation
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 369-393
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  • 4
    Publikationsdatum: 2005-11-27
    Beschreibung: Design criteria for onboard centrifuges in orbital space stations to create artificial gravity
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 329-346
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  • 5
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Jet induced flow field effects on V/STOL aircraft in subsonic transition flight
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 683-702
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  • 6
    Publikationsdatum: 2005-11-27
    Beschreibung: Linear acceleration effects on semicircular canals in elasmobranch fishes
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 159-166
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  • 7
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Neurological elements in vomiting sequence and components of emetic reflex in motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 117-120
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  • 8
    Publikationsdatum: 2005-11-27
    Beschreibung: Iterative method for designing supersonic body of revolution from surface pressure distribution
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 75-84
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  • 9
    Publikationsdatum: 2005-11-30
    Beschreibung: The biostack experiment is described which was designed to study the biologic effects of individual heavy nuclei of galactic cosmic radiation during space flight outside the magnetosphere of the earth. Specifically, the biostack experiment was designed to promote research on the effects of high energy/high Z particles of galactic cosmic radiation on a broad spectrum of biologic systems, from the molecular to the highly organized and developed forms of life. The experiment was considered unique and scientifically meritorious because of its potential yield of information - currently unavailable on earth - on the interaction of biologic systems with the heavy particles of galactic cosmic radiation.
    Schlagwort(e): BIOSCIENCES
    Materialart: NASA. Lyndon B. Johnson Space Center Apollo 16 Prelim. Sci. Rept.; 10 p
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  • 10
    Publikationsdatum: 2005-11-30
    Beschreibung: Microbial analysis was the first of several studies of the retrieved camera and was performed immediately after the camera was opened. The emphasis of the analysis was placed upon isolating microorganisms that could be potentially pathogenic for man. Every step in the retrieval of the Surveyor 3 television camera was analyzed for possible contamination sources, including camera contact by the astronauts, ingassing in the lunar and command module during the mission or at splashdown, and handling during quarantine, disassembly, and analysis at the Lunar Receiving Laboratory
    Schlagwort(e): BIOSCIENCES
    Materialart: Analysis of Surveyor 3 Mater. and Phot. Returned by Apollo 12; p 239-248
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  • 11
    Publikationsdatum: 2005-11-27
    Beschreibung: Dynamic response of semicircular canals to constant rotation in linear acceleration field
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 353-362
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  • 12
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Ground wind loads on reusable space shuttles
    Schlagwort(e): AERODYNAMICS
    Materialart: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 143-160
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  • 13
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Extralabyrinthine influences as secondary etiological factors in susceptibility to motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 83-88
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  • 14
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Space shuttle buffeting and aerodynamic noise
    Schlagwort(e): AERODYNAMICS
    Materialart: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 238-247
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  • 15
    Publikationsdatum: 2005-11-27
    Beschreibung: Ducted fan interference analysis for transport aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 703-719
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  • 16
    Publikationsdatum: 2005-11-27
    Beschreibung: Time-dependent numerical method for blunt body flow field solutions
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 177-195
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  • 17
    Publikationsdatum: 2005-11-27
    Beschreibung: Prediction methods for boundary layer and flow field characteristics in shock wave-boundary layer interaction
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 515-539
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  • 18
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical analysis of three dimensional viscous supersonic flow fields about slender bodies
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 265-321
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  • 19
    Publikationsdatum: 2005-11-30
    Beschreibung: The performance of the microbial response to space environment experiment is considered excellent by all investigators. For most microbial systems, only preliminary survival data are available at this time. None of the available data indicate space flight-mediated changes in cell viability or recovery. One quite important observation has been made at this early date, however. The eggs produced after mice had been infected with N. dubius larvae demonstrated a significant decrease in hatchability when compared to identical ground controls. Except for the fact that the Apollo 16 flight larvae had been on board the command module, treatment of the flown larvae and ground control larvae was the same; neither had been exposed to UV irradiation. The significance and implications of this finding are currently being studied.
    Schlagwort(e): BIOSCIENCES
    Materialart: Apollo 16 Prelim. Sci. Rept.; 6 p
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  • 20
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    In:  CASI
    Publikationsdatum: 2005-11-30
    Beschreibung: The Apollo 16 mission provided the opportunity to obtain additional data on the characteristics and frequency of the light flashes and also provided the first opportunity to obtain a direct physical record of incident cosmic ray particles with the Apollo light flash moving emulsion detector (ALFMED). The ALFMED is an electromechanical device that is worn on the head like a helmet and supports cosmic radiation-sensitive emulsions around the head of the test subject. Two light flash observation sessions were conducted during the mission: one during translunar coast and the second during transearth coast. Characteristics of the light flashes observed and reported by the Apollo crew members were generally similar to those reported on previous missions. Analyses of the ALFMED emulsion plates are proceeding as scheduled, although results are not yet available. The ALFMED results should provide conclusive evidence establishing the correlation, if any, between the incident cosmic ray particles and the perception of light flashes as reported by Apollo crew members.
    Schlagwort(e): BIOSCIENCES
    Materialart: Apollo 16 Prelim. Sci. Rept.; 4 p
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  • 21
    Publikationsdatum: 2005-11-30
    Beschreibung: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA Space Shuttle Technol. Conf.; p 71-96
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  • 22
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Linear acceleration movements as eliciting mechanism of motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 7-28
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  • 23
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Energy requirements for walking in simulated lunar gravity
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 347-352
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  • 24
    Publikationsdatum: 2005-11-27
    Beschreibung: Experimental and clinical treatment of Meniere's disease using ultrasonic radiation
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 269-284
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  • 25
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Postsynaptic effects of vestibular and cerebellar impulses in vestibular nuclei neurons of cat
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 183-200
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  • 26
    Publikationsdatum: 2005-11-27
    Beschreibung: Computer analysis of single-unit discharges in vestibular nerve of frog
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 137-144
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  • 27
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Inadequate and inappropriate vascular and circulatory responses as causative factors in motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 89-98
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  • 28
    Publikationsdatum: 2005-11-27
    Beschreibung: Otolith organs as primary etiological factor in motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 53-66
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  • 29
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Life support systems and space suits for preserving homeostatic reactions of astronauts
    Schlagwort(e): BIOSCIENCES
    Materialart: TRANS. OF THE FIRST LECTURES DEDICATED'TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOUSKIY APR. 1970; P 91-98
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  • 30
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for computerized design of optimal supersonic inlets
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 569-581
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  • 31
    Publikationsdatum: 2005-11-27
    Beschreibung: Aerodynamic method of characteristics for pressure field calculations about wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: L METHODS IN AIRCRAFT AERODYN. 1970; P 215-227
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  • 32
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical analysis of propeller-wing flow interaction with slipstreams
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 721-742
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  • 33
    Publikationsdatum: 2005-11-30
    Beschreibung: A piece of electrical wiring bundle running from the television camera to another part of the spacecraft was selected for microbiological examination. Sampling methods are discussed. The results presented show that no viable microorganisms were recovered from the part of the Surveyor 3 cable which was tested. Factors that could have contributed to the sterility of the cable are thermal vacuum testing, natural dieoff, change in pressure during launch, and lunar vacuum and temperature.
    Schlagwort(e): BIOSCIENCES
    Materialart: NASA, Washington Analysis of Surveyor 3 Mater. and Phot. Returned by Apollo 12; p 248-251
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  • 34
    Publikationsdatum: 2005-11-27
    Beschreibung: Wind tunnel simulation of ground wind shear and turbulence spectra and application to space shuttle launching
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 161-175
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  • 35
    Publikationsdatum: 2005-11-27
    Beschreibung: Perception thresholds of rotation about three major body axes
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 299-306
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  • 36
    Publikationsdatum: 2005-11-27
    Beschreibung: Multisensory stimulation effects on single units in vestibular nucleus of cat
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 201-208
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  • 37
    Publikationsdatum: 2005-11-27
    Beschreibung: Preventing motion sickness in slow rotation room by incremental increases in strength of stimulus
    Schlagwort(e): BIOSCIENCES
    Materialart: SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 109-116
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  • 38
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Vestibular activity in descending medial longitudinal fasciculus
    Schlagwort(e): BIOSCIENCES
    Materialart: SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 237-242
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  • 39
    Publikationsdatum: 2005-11-27
    Beschreibung: Functional organization of vestibulospinal projection in ear, emphasizing sites of termination
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 167-182
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  • 40
    Publikationsdatum: 2005-11-27
    Beschreibung: Lift and pressure distribution calculations for winged body with leading edge vortices
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 113-129
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  • 41
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Scopolamine and d-amphetamine in prevention of motion sickness
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 99-108
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  • 42
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Motion sickness susceptibility related to wave character and effects of sickness on performance
    Schlagwort(e): BIOSCIENCES
    Materialart: NAVAL AEROSPACE MED. INST. 4TH SYMP. ON THE ROLE OF THE VESTIBULAR ORGANS IN SPACE EXPLORATION 1970; P 29-32
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  • 43
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference solution for compressible turbulent boundary layer equations of swept slab with leading edge blowing
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 417-472
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  • 44
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Review of prediction methods for compressible turbulent boundary layers
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 355-416
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  • 45
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference analysis of hyperbolic partial differential equations
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 245-264
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  • 46
    Publikationsdatum: 2005-11-27
    Beschreibung: Computer programs for predicting flow field properties in supersonic and hypersonic inlets
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 583-595
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  • 47
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Wing-body interference theory for calculating lift slope and stability at hypersonic speed
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 101-111
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  • 48
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Numerical lifting surface theory with spanwise distribution of control points
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 1-35
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  • 49
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for flow field analysis on elliptical winged body
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 159-176
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  • 50
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite element method for predicting aerodynamic characteristics of wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 37-51
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  • 51
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Potential flow solution for VTOL inlets in static and crossflow operation
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 659-681
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  • 52
    Publikationsdatum: 2005-11-27
    Beschreibung: Analysis of secondary flow effects in propeller and rotor boundary layers
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 473-514
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  • 53
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Finite difference method for transonic flow solution in axial stator
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 597-621
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  • 54
    Publikationsdatum: 2005-11-27
    Beschreibung: Method of characteristics for calculating oblique shock wave interaction with turbulent boundary layer
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 541-567
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  • 55
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Aerodynamic forces in supersonic panel flutter
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 335-353
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  • 56
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Static laminar Coanda jet flow around circular cylinder with external flow entrainment
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 197-214
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  • 57
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Correlation method for estimating pressure distribution over elliptic supersonic cones
    Schlagwort(e): AERODYNAMICS
    Materialart: L. METHODS IN AIRCRAFT AERODYN. 1970; P 85-99
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  • 58
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    In:  CASI
    Publikationsdatum: 2005-11-27
    Beschreibung: Calculation methods for predicting transonic aerodynamic characteristics of wing-body combinations
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 53-73
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  • 59
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    In:  CASI
    Publikationsdatum: 2009-11-17
    Beschreibung: Psychological factors of prolonged space flight on astronaut performance
    Schlagwort(e): BIOSCIENCES
    Materialart: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 98-105
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  • 60
    Publikationsdatum: 2009-11-17
    Beschreibung: Prediction of steady and unsteady airloads on space shuttles
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 223-237
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  • 61
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    In:  CASI
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 121-133
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  • 62
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
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  • 63
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    In:  CASI
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 49-58
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  • 64
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    In:  CASI
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 71-84
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  • 65
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 85-96
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  • 66
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    In:  CASI
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 1-12
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  • 67
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    In:  CASI
    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 35-48
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  • 68
    Publikationsdatum: 2006-02-14
    Beschreibung: A joint NASA/U.S. industry program to test advanced technology airfoils in the Langley 0.3-meter Transonic Tunnel (TCT) was formulated under the Langley ACEE Project Office. The objectives include providing U.S. industry an opportunity to compare their most advanced airfoils to the latest NASA designs by means of high Reynolds number tests in the same facility. At the same time, industry would again experience in the design and construction of cryogenic test techniques. The status and details of the test program are presented. Typical aerodynamic results obtained, to date, are presented at chord Reynolds number up to 45 x 10(6) and are compared to results from other facilities and theory. Details of a joint agreement between NASA and the Deutsche Forschungs- und Versuchsantalt fur Luft- and Raumfahrt e.V. (DFVLR) for tests of two airfoils are also included. Results of these tests will be made available as soon as practical.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advan. Aerodyn.: Selected NASA Res.; p 37-53
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  • 69
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    In:  CASI
    Publikationsdatum: 2006-04-26
    Beschreibung: Helicopter crew and passenger vibration sensitivity are presented. Pilot subjective ratings are established for discrete frequencies and the impact of combinations of harmonic frequencies is examined. A passenger long term comfort level and a short term limit are defined for discrete frequencies and compared with pilot ratings. The results show reasonable agreement between pilot and passenger. Subjective comfort levels obtained for mixed frequency environments clearly demonstrate the need for a multi-frequency criterion.
    Schlagwort(e): BIOSCIENCES
    Materialart: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 143-153
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  • 70
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    Publikationsdatum: 2006-04-25
    Beschreibung: Component connection schemes of brain for trainable feedback flight control system
    Schlagwort(e): BIOSCIENCES
    Materialart: NIFICANT ACCOMPLISHMENTS IN SCI. AND TECHNOL. AT GODDARD SPACE FLIGHT CENTER 1970; P 292-294
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  • 71
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    In:  CASI
    Publikationsdatum: 2006-02-14
    Beschreibung: Dynamic model verification is the process whereby an analytical model of a dynamic system is compared with experimental data, adjusted if necessary to bring it into agreement with the data, and then qualified for future use in predicting system response in a different dynamic environment. These are various ways to conduct model verification. The approach taken here employs Bayesian statistical parameter estimation. Unlike curve fitting, whose objective is to minimize the difference between some analytical function and a given quantity of test data (or curve), Bayesian estimation attempts also to minimize the difference between the parameter values of that funciton (the model) and their initial estimates, in a least squares sense. The objectives of dynamic model verification, therefore, are to produce a model which: (1) is in agreement with test data; (2) will assist in the interpretation of test data; (3) can be used to help verify a design; (4) will reliably predict performance; and (5) in the case of space structures, will facilitate dynamic control.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 15 p
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  • 72
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    Publikationsdatum: 2006-02-14
    Beschreibung: Multidisciplinary analysis often requires optimization of nonlinear systems that are subject to constraints. Trajectory optimization is one example of this situation. The Program to Optimize Simulated Trajectories (POST) was used successfully for a number of problems. The purpose is to describe POST and a new optimization approach that has been incorporated into it. Typical uses of POST will also be illustrated. The projected-gradient approach to optimization is the preferred option in POST and is discussed. A new approach to optimization, the random-walk approach, is described, and results with the random-walk approach are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 23 p
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  • 73
    Publikationsdatum: 2006-02-14
    Beschreibung: The purpose is not to provide a detailed discussion of several wall interference experiments, but rather to use these experiments (recently accomplished in the Boeing Transonic Wind Tunnel (BTWT) to illustrate the problems associated with many of the measurements required by current wall interference assessment/correction (WIAC) procedures. The wall correction to lift is emphasized. It is shown that, because conventional tunnels and relatively small models continue to be used, the flow field or flow boundary measurements to be made impose severe requirements on the experiment itself. In some cases, existing instrumentation and test techniques may not be adequate to obtain the data accuracies needed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 21-42
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  • 74
    Publikationsdatum: 2006-02-14
    Beschreibung: Based upon limited, initial observations of wall interference corrections obtained for one airfoil test, there is a need for assessing the upstream flow direction. If there is no direct measurement then a two-pass correction procedure similar to the one described here is required. Questions have arisen pertaining to the correct interpretation of the pressure coefficients measured on the slats of a slotted tunnel wall, the interpretation of just what the calculated equivalent body encompasses or should include, and what can or should be considered as quantitative criteria for data correctability. Further studies using this modified procedure will address these questions. Hopefully, a meaningful WIAC procedure can be validated for the airfoil tests in the 0.3-m TCT.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 393-414
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  • 75
    Publikationsdatum: 2006-02-14
    Beschreibung: A series of airfoils were tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT) at Reynolds numbers from 2 to 50 million. The 0.3-m TCT is equipped with Barnwell slots designed to minimize blockage due to the tunnel flow and ceiling. This design suggests that sidewall corrections for blockage is needed, and that a lifting airfoil produces a change in angle of attack. Sidewall correction methods were developed for subsonic and subsonic-transonic flow. Comparisons of theory with experimental data obtained in the 0.3-m TCT for two airfoils, the British NPL 9510 and the German R-4 are presented. The NPL 9510 was tested as part of the NASA/United Kingdom Joint Aeronautical Program and R-4 was tested as part f the DFVLR/NASA Advanced Airfoil Research Program. For the NPL 9510 airfoil, only those test points that one would anticipate being difficult to predict theoretically are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 375-392
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  • 76
    Publikationsdatum: 2006-02-14
    Beschreibung: Representation of the flow around full-scale ships was sought in the subsonic wind tunnels in order to a Hain Reynolds numbers as high as possible. As part of the quest to attain the largest possible Reynolds number, large models with high blockage are used which result in significant wall interference effects. Some experiences with such a high blockage model tested in the NASA Ames 12-foot pressure wind tunnel are summarized. The main results of the experiment relating to wind tunnel wall interference effects are also presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 345-360
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  • 77
    Publikationsdatum: 2006-02-14
    Beschreibung: The various procedures referred to as wall interference assessment and correction procedures presume the existence of a surface distribution of data (usually static pressure) measured over a surface on or near the tunnel walls for each test point to be assessed. An alternative approach in which a reasonably sophisticated computer model of the test section flow would be fitted parametrically to a sparse set of measured data is presented. The measurements provides line distributions of static pressure near the center lines of the top, side and bottom walls. The development of a test section model incorporating explicit recognition of discrete slots of finite length with controlled flow reentry into the solid wall downstream portion of the tunnel is shown.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 323-334
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  • 78
    Publikationsdatum: 2006-03-27
    Beschreibung: Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 455-473
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  • 79
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    Publikationsdatum: 2006-03-27
    Beschreibung: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 413-426
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  • 80
    Publikationsdatum: 2006-03-27
    Beschreibung: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 443-454
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  • 81
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    Publikationsdatum: 2006-03-27
    Beschreibung: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 427-441
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  • 82
    Publikationsdatum: 2006-03-27
    Beschreibung: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 143-156
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  • 83
    Publikationsdatum: 2006-03-27
    Beschreibung: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 157-800
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  • 84
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    Publikationsdatum: 2006-03-27
    Beschreibung: The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center STOL Technol.; p 97-110
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  • 85
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    Publikationsdatum: 2006-03-27
    Beschreibung: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 87-96
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  • 86
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    Publikationsdatum: 2006-03-27
    Beschreibung: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 71-86
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  • 87
    Publikationsdatum: 2006-03-27
    Beschreibung: Small-scale-model data have shown large static loads on the flap system behind the engines. The large-scale-model tests confirmed the magnitude of these loads and indicated that the relative loading of each flap element depends on the engine-wing-flap geometry. Flap response measurements indicated that the unsteady pressure loading excited the natural vibration modes of the flap system on this model. Since this was a boilerplate model, the only conclusion that can be drawn is that the possibility of large vibration loads must be considered for a flight-weight structure. The similarity of the unsteady pressure and flap response spectra for the wind-off and wind-on cases indicated that it may be possible to realistically test flight-weight flap structures on a static test stand rather than endure the extra costs and scheduling problems associated with large-scale wind-tunnel tests. There is a potential flap-temperature problem which if not resolved might preclude the use of materials such as aluminum and the composites in the flap structure.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 121-130
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  • 88
    Publikationsdatum: 2006-03-27
    Beschreibung: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 43-54
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  • 89
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    Publikationsdatum: 2006-03-27
    Beschreibung: The results of wind-tunnel investigations on the stability and control characteristics of externally blown jet-flap configurations are presented. Conventional wind-tunnel tests and free-flight model tests have shown that longitudinal trim and stability can be achieved by a properly located horizontal tail of sufficient size, and that lateral trim in the engine-out condition can be produced by combinations of differential flap, spoiler, and rudder deflection. Free-flight model tests have revealed a lightly damped Dutch roll lateral oscillation, and have shown that the oscillation can be stabilized by use of artificial damping.
    Schlagwort(e): AERODYNAMICS
    Materialart: STOL Technol.; p 55-70
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  • 90
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    In:  CASI
    Publikationsdatum: 2006-02-14
    Beschreibung: Wall interference is made predominant in tunnel models and by wall geometries to facilitate the study of slot flow. The viscous effects in slots are studied by two dimensional measurements of flow. Wall interference is assessed by measuring pressure distributions at two levels near the walls. Interference on lifting delta wings is calculated. Pressure distributions at inner boundaries show basis axisymetries between the pressure side and the suction side, pointing to the necessity of having wider slots on the pressure side.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 293-300
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  • 91
    Publikationsdatum: 2006-02-14
    Beschreibung: Classical methods for calculation of wall corrections which are not satisfactory for a number of flows of interest are discussed. To meet these objections, a number of methods were developed which use measurements of the low at or close to the tunnel walls as an outer boundary condition to define wall interference. The development, assessment and application of one such method is summarized.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 259-271
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  • 92
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    Publikationsdatum: 2006-02-14
    Beschreibung: Measured field data as a boundary condition for calculating the interference flow field were applied. They are divided into two categories. In the first category, the field data must consist of distributions of a single velocity component, and an accurate estimate of the hypothetical free air contribution of the model to this component is required. The differences between measured values and estimated model contributions are attributed to wall interference and they establish the boundary condition. The associated field data measurements are simple, yet the necessary model representation generally is a serious drawback. The second category requires field data which consist of velocity vector distributions at the price of multicomponent measurements, but at the profit that no information at all is required about the model. In solid wall test sections, the price is reduced to virtually zero but the profit remains.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 221-229
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  • 93
    Publikationsdatum: 2006-02-14
    Beschreibung: A limited-zone ventilated wall panel was developed for a closed-wall icing tunnel which permitted correct simulation of transonic flow over model rotor airfoil sections with and without ice accretions. Candidate porous panels were tested in the Ohio State University 6- x 12-inch transonic airfoil tunnel and result in essentially interference-free flow, as evidenced by pressure distributions over a NACA 0012 airfoil for Mach numbers up to 0.75. Application to the NRC 12- x 12-inch icing tunnel showed a similar result, which allowed proper transonic flow simulation in that tunnel over its full speed range.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 165-170
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  • 94
    Publikationsdatum: 2006-02-14
    Beschreibung: The free-stream interference caused by the flow through the slotted walls of the test sections of transonic wind tunnels has continuously a problem in transonic tunnel testing. The adaptive-wall transonic tunnel is designed to actively control the near-wall boundary conditions by sucking or blowing through the wall. In order to make the adaptive-wall concept work, parameters for computational boundary conditions must be known. These parameters must be measured with sufficient accuracy to allow numerical convergence of the flow field computations and must be measured in an inviscid region away from the model that is placed inside the wind tunnel. The near-wall flow field was mapped in detail using a five-port cone probe that was traversed in a plane transverse to the free-stream flow. The initial experiments were made using a single slot and recent measurements used multiple slots, all with the tunnel empty. The projection of the flow field velocity vectors on the transverse plane revealed the presence of a vortex-like flow with vorticity in the free stream. The current research involves the measurement of the flow field above a multislotted system with segmented plenums behind it, in which the flow is controlled through several plenums simultaneously. This system would be used to control a three-dimensional flow field.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 119-142
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  • 95
    Publikationsdatum: 2006-02-14
    Beschreibung: A three-dimensional adaptive-wall wind tunnel experiment was conducted at Ames Research Center. This experiment demonstrated the effects of wall interference on the upwash distribution on an imaginary surface surrounding a lifting wing. This presentation demonstrates how the interference assessment procedure used in the adaptive-wall experiments to determine the wall adjustments can be used to separately assess lift- and blockage-induced wall interference in a passive-wall wind tunnel. The effects of lift interference on the upwash distribution and on the model lift coefficient are interpreted by a simple horseshoe vortex analysis.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 89-100
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  • 96
    Publikationsdatum: 2006-02-14
    Beschreibung: A wall interference correction method for closed rectangular test sections was developed which uses measured wall pressures. Measurements with circular discs for blockage and a rectangular wing as a lift generator in a square closed test section validate this method. These measurements are intended to be a basis of comparison for measurements in the same tunnel using ventilated (in these case, slotted) walls. Using the vortex lattice method and homogeneous boundary conditions, calculations were performed which show sufficiently high pressure levels at the walls for correction purposes in test sections with porous walls. In Gottingen, an adaptive test section (which is a deformable rubber tube of 800 mm diameter) was built and a computer program was developed which is able to find the necessary wall adaptation for interference-free measurements in a single step. To check the program prior to the first run, the vortex lattice method was used to calculate wall pressure distributions in the nonadapted test section as input data for the one-step method. Comparison of the pressure distribution in the adapted test section with free-flight data shows nearly perfect agreement. An extension of the computer program can be made to evaluate the remaining interference corrections.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 61-78
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  • 97
    Publikationsdatum: 2006-02-14
    Beschreibung: The following areas were addressed: interchangeable test sections in the 0.3-M Transonic Cryogenic Tunnel (TCT); typical airfoil installation; airfoil capability; advanced technology airfoil test (ATAT); effects of the Reynolds number on the normal force coefficient; effects of the Reynolds number on the drag coefficient; and comparison of experimental results with theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 361-374
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    Standort Signatur Erwartet Verfügbarkeit
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  • 98
    Publikationsdatum: 2006-02-14
    Beschreibung: A formula for the determination of equivalent model geometry with two variables measured at the interface is derived, based on two dimensional subsonic flow. This predicted model profile is a reasonable initial estimate for transonic flow as long as the sonic region does not reach the interface. A general formula is given in two forms. One is in terms of complex variable functions and the other is an integral equation. The complex-function formula has the advantage of using analytic expressions. The integral equation form requires a numerical solution after assuming the model geometry as a polynomial function. Examples are given to illustrate the application of the formulas.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 335-342
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  • 99
    Publikationsdatum: 2006-02-14
    Beschreibung: Wall interference correction procedures seek to determine the required changes in certain flow or geometric parameters so that the difference between the flow properties at the model's surface in the tunnel and free air are minimized. A transonic and a linear correction procedure were developed for aircraft models. In addition to Mach number and angle of attack corrections, an estimate of the accuracy of the corrections is provided by the transonic correction procedure. Lift, pitching moment and pressure measurements near the tunnel walls are required. The efficiency and accuracy of the correction procedure are improved. Moreover, correction of both the wing and tail angles of attack is allowed. The procedure is valid for transonic as well as subcritical flows. However, for subcritical flows further approximations and simplifying assumptions are made, leading to a very simple and efficient correction procedure.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 301-322
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  • 100
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2006-02-14
    Beschreibung: A facet of a unified tunnel correction scheme which uses wall pressures to determine tunnel induced blockage and upwash is described. With this method, there is usually no need to use data concerning model forces or power settings to find the interference; it follows directly from the pressures and tunnel dimensions. However, highly inclined jets do not produce good pressure signatures and are highly three dimensional, so they must be treated differently. Flow modeling is also discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 273-290
    Format: text
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